US 6,354,795 B1Granted

Shroud cooling segment and assembly

AssigneeGeneral Electric Company

InventorsGregory Alan White, Ching-Pang Lee

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Abstract

A cooling shroud segment for a high pressure turbine that provides improved cooling in the region of the side panels from the midsection thereof forward to the leading edge and particularly in the midsection of the side panel. A shroud subassembly can be formed from a pair of such adjacent shroud segments with opposed adjacent side panels where the spacing of the outlets of the cooling air passages exiting from each of these adjacent side panels are staggered and where the adjacent panels have a spline seal slot with a humped section in at least the midsection of the side panel above and across the outlets of the cooling air passages exiting from the midsection of the side panel, in combination with a spline seal positioned in the gap between the opposed adjacent side panels. This shroud subassembly provides more uniform impingement cooling coverage and localizes more of the cooling air exiting the outlets from these passages in the midsection of the opposed side panels.

Claims15

Dependent claims

A turbine cooling component for a turbine engine, which comprises:

(a) a circumferential leading edge;
(b) a circumferential trailing edge spaced from the leading edge;
(c) an arcuate base connected to the trailing and leading edges and having a back surface and an arcuate inner surface that is in contact with the main hot gas stream of the turbine engine moving in the direction from the leading edge to the trailing edge of the turbine component;
(d) a pair of spaced opposed side panels connected to the leading and trailing edges, each of the side panels having a leading section, a midsection and trailing section;
(e) a plurality of cooling air passages extending through the base from the back surface thereof and having outlets exiting from at least one of the leading edge, the side panels and the inner surface of the base;
(f) wherein all of the plurality of cooling air passages having outlets that exit from the leading or midsections of each side panel are skewed so that cooling air exits therefrom in a direction opposed to the main hot gas stream;
(g) wherein at least one of the plurality of cooling air passages is an impingement cooling air passage, which has an outlet that exits from the midsection of one of the side panels and wherein at least another of the plurality of cooling air passages is an impingement cooling air passage, which has an outlet that exits from the midsection of the other side panel, and
(h) a spline seal slot that extends from the leading section to the trailing section of each side panel, the slot having a humped section in at least the midsection of the side panel that is above and across at least the outlets of the cooling air passages exiting from the midsection of the side panel.

5 more elements

A turbine cooling subassembly for a turbine engine, which comprises:

(a) a pair of adjacent turbine cooling components, each of the turbine components comprising:
(1) a circumferential leading edge;
(2) a circumferential trailing edge spaced from the leading edge;
(3) an arcuate base connected to the trailing and leading edges and having a back surface and an arcuate inner surface that is in contact with the main gas stream of the turbine engine moving in the direction from the leading edge to the trailing edge of the turbine component;
(4) a pair of spaced opposed side panels connected to the leading and trailing edges, each of the side panels having a leading section, a midsection and trailing section;
(5) a plurality of cooling air passages extending through the base from the back surface thereof and having outlets exiting from at least one of the leading edge, the side panels and the inner surface of the base;
(6) wherein all of the plurality of cooling air passages that have outlets that exit from the leading or midsections of each side panel are skewed so that the cooling air exits therefrom in a direction opposed to the main hot gas stream;
and
(7) wherein at least one of the plurality of cooling air passages has an outlet that exits from the midsection of each side panel;
(b) wherein opposed adjacent side panels of the pair of turbine components have a gap therebetween and wherein the outlets of cooling air passages exiting from each of the adjacent side panels is spaced such that outlets of each cooling air passage exiting from one of the adjacent panels is not directly opposite the outlets of the cooling air passages exiting from the other of the adjacent panels;
(c) each of the opposed adjacent side panels of the pair of shroud segment having a spline seal slot that extends from the leading section to the trailing section of the side panel, the slot having a humped section in at least the midsection of the side panel that is above and across at least the outlets of the cooling air passages exiting from the midsection of the side panel;
and
(d) at least one spline seal positioned in the gap between the opposed adjacent side panels and including a pair of spaced edges having a length and thickness such that each of the edges is capable of being received by the slot of one of the adjacent side panels.

10 more elements

Dependencies are inferred from the claim text.